Triple Flywheel Assembly for Attitude Jitter Minimization
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Solution Overview
Problem
Existing flywheel systems in satellites suffer from imbalance, leading to high-frequency oscillations known as jitter, which degrade the performance of payloads such as telescopes and communication equipment, and current jitter mitigation methods either isolate the effect or do not address the source of jitter effectively.
Innovation Solution
A three-flywheel system is introduced, where each flywheel is axially aligned and independently controlled to manipulate the phase difference between them, actively reducing the amplitude of attitude jitter by achieving static and dynamic balance, thereby minimizing jitter at its source.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single flywheel system is used for attitude control, then the device complexity is low, but jitter is generated due to imbalance and loss of symmetry over time
Solution Approach 1:
The single flywheel system is segmented into three separate flywheels (first, second, and third flywheels) that are axially aligned and independently controllable. Each flywheel can be individually adjusted to manipulate phase differences, allowing the system to counteract imbalance and reduce jitter while maintaining manageable complexity through modular architecture.
2Object-affected harmful factors
If passive isolators are used to minimize jitter, then the harmful effects on payloads are reduced, but the stiffness of supports is reduced and payload is vulnerable to large displacements
Solution Approach 1:
Instead of isolating the payload from jitter using passive isolators that reduce support stiffness, the invention converts the harmful imbalance forces into a beneficial control mechanism. The three-flywheel system uses independent phase manipulation to actively counteract jitter at its source, transforming the problem of imbalance into a solution where controlled phase differences eliminate vibrations while maintaining rigid support structures.
3Object-affected harmful factors
If active isolators are used to compensate for jitter, then jitter compensation is achieved, but the system requires continuous power and additional mass
Solution Approach 1:
The three-flywheel system is self-service in that it uses its own components (the three flywheels) to generate the counteracting forces needed for jitter reduction. By independently controlling the phase of each flywheel, the system creates internal balance forces that eliminate jitter without requiring external active isolators, continuous power input for compensation, or additional mass beyond the three flywheels themselves.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The three-flywheel system significantly reduces jitter compared to traditional single-flywheel systems, achieving complete balance and providing redundancy, which enhances the stability and reliability of satellite pointing performance while maintaining comparable power and mass characteristics.
Implementation Method 1
The CMG has flywheels mounted on gimbals which when actuated produce gyroscopic torque that is the control input for the attitude control system (ACS)
Implementation Method 2
A large amount of momentum must be stored in these flywheels to be able to produce torques large enough to achieve rapid retargeting
Implementation Method 3
A single flywheel system may not maintain perfect balance during use... Any imbalance or loss of symmetry in the flywheel system may cause disturbances which may result in high frequency oscillations
Data Source
AI summary
Various embodiments of the present invention include assemblies and methods for minimizing the amplitude of attitude jitter. In one embodiment, a flywheel assembly for reducing the amplitude of attitude jitter is provided. The flywheel assembly includes a first flywheel, a second flywheel, and a third flywheel. The first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another. Each flywheel is configured to be independently controlled in order to manipulate the phase difference therebetween.